矢量电推进系统的气动-推进耦合模型  

Aerodynamic/propulsion coupling model of vector electric propulsion system

作　　者：夏济宇 周洲[1] 徐德 王正平[1] XIA Jiyu;ZHOU Zhou;XU De;WANG Zhengping(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空学报》2023年第11期135-147,共13页Acta Aeronautica et Astronautica Sinica

基　　金：国防基金(2021-JCJQ-JJ-0805);陕西省重点研发计划(2021ZDLGY09-08)。

摘　　要：提出了一种适用于矢量电推进系统的气动-推进耦合模型,旨在通过结合理论模型与工程经验模型,实现对矢量电推进系统气动与推进性能的实时快速评估。为了准确描述系统的气动-推进耦合效应,首先,结合涵道推进增强系数公式与工程经验模型,建立涵道推进模型;紧接着建立了涵道气动模型,并基于推进效应影响完成了模型修正;然后,分析了涵道气流抽吸效应对机翼的影响,根据涵道是否倾转分别进行了讨论,完成了耦合推进系统的机翼增升模型的建立;最后,将所有模型统一至机体坐标系下,得到矢量电推进系统的气动-推进耦合模型,并依据CFD仿真计算进行了模型验证与分析。结果表明:所提出的气动-推进耦合模型可以准确描述涵道增推与机翼增升效应,能在极快的运算速度下保持较高精度,满足动力学系统与飞行控制系统的实时计算要求。This paper proposes an aerodynamic/propulsion coupling model to realize real-time and rapid evaluation of the aerodynamic and propulsion performance of the vector electric propulsion system by combining the theoretical model with the engineering experience model.To accurately describe the aerodynamic/propulsion coupling effect of the system,we first establish the propulsion model of the ducted fan by combining the propulsion enhancement coeffi⁃cient formula and the engineering experience model.The aerodynamic model of the ducted fan is then established and modified based on the propulsion influence.Afterwards,the influence of the suction effect induced by the ducted fan on the wing is analyzed,and the coupled propulsion lift enhancement model of the wing established according to the tilting of the ducted fan.Finally,through integration of all the models into the airframe coordinate system,the aerody⁃namic/propulsion coupling model of the vector electric propulsion system is obtained,subsequently verified,and ana⁃lyzed based on the CFD simulation.The results show that the aerodynamic/propulsion coupling model proposed in this paper can accurately describe the thrust enhancement of the duct and the lift enhancement of the wing,maintaining high accuracy with extremely fast computing speed and meeting the real-time computing requirements of the dynamics system and flight control system.

关 键 词：电推进系统 气动-推进耦合 实时计算 电动涵道 机翼增升 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]